CN115570105B - Manufacturing method of double-wall turbine blade - Google Patents
Manufacturing method of double-wall turbine blade Download PDFInfo
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- CN115570105B CN115570105B CN202211451891.3A CN202211451891A CN115570105B CN 115570105 B CN115570105 B CN 115570105B CN 202211451891 A CN202211451891 A CN 202211451891A CN 115570105 B CN115570105 B CN 115570105B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/22—Moulds for peculiarly-shaped castings
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention relates to the field of aviation design and manufacturing, and discloses a manufacturing method of a double-wall turbine blade, wherein under the given design boundary conditions, the cooling structure size meeting the cooling design requirement of the blade is calculated and obtained according to the flow coefficient and heat exchange coefficient of a double-wall impact turbulence structure; and preparing a blade core which can be cast into a structure with the turbulent flow column and the inner wall cooling channel according to the sizes of the impact hole, the turbulent flow column and the cooling channel which meet the requirements, and then adopting a wax losing method to cast and mold the double-wall turbine blade. According to the invention, according to the flow coefficient and the heat exchange coefficient, the calculation experience is correlated, the cooling structure size meeting the cooling design requirement of the blade is obtained under the given design boundary condition, the micro-scale structure of the double-wall turbine blade core is obtained in an optimized way, the double-wall turbine blade is obtained through lost wax casting, and the double-wall turbine blade structure with more efficient cooling effect can be obtained.
Description
Technical Field
The invention relates to the technical field of aeroengines, in particular to a manufacturing method of a double-wall turbine blade.
Background
In high performance aeroengines, since the turbine inlet gas temperature far exceeds the bearing limit of the turbine blade materials, effective cooling measures must be employed to ensure reliable operation of the turbine blades in high temperature, high pressure and high rotational speed environments. At present, the turbine blade of the aeroengine generally adopts the technology such as ultrahigh temperature heat-resistant alloy, single crystal metallographic structure, composite air film cooling type hollow structure and the like so as to meet the performance requirements of the turbine blade at high temperature and high pressure. The complexity of the material and the mechanism results in lower qualification rate of the existing hollow turbine blade precision casting blank, which is only 10 percent. The key technology of the manufacture of the high-efficiency air-cooled blade is that the ceramic core is manufactured, and the ceramic core has good refractoriness, room temperature strength, high temperature heat stability, void fraction and core stripping performance.
The actual wall of present high performance turbine blade is thinner, adopts double-deck wall structure moreover, compares with traditional hollow blade, and ceramic core structure is more complicated, and the wall thickness is thinner, and the difference is bigger, needs to adopt more advanced more complicated microchannel cooling design, and higher casting pressure satisfies more efficient cooling demand. Meanwhile, the core of the cast blade is large in deformation and difficult to control in the manufacturing process, the deformation of the core is easy to cause in positioning, and the micro-channel cooling structures such as the small-size turbulent flow column and the like are easy to crack, deform and even break in the manufacturing process, so that the quality and the qualification rate of the turbine blade are seriously affected.
Disclosure of Invention
In view of the above, the invention provides a manufacturing method of a double-wall turbine blade, which is characterized in that the core size suitable for the double-wall turbine blade is determined by introducing flow coefficient and heat exchange coefficient calculation experience association, and the cooling effect is better while the strength requirement is met.
A method of manufacturing a double-walled turbine blade comprising the steps of:
step 1, determining a double-wall turbine blade core base material and size and cooling design parameters of a blade according to the design size and cooling design requirements of the double-wall turbine blade, wherein the cooling design parameters comprise the temperature and pressure of cool air at the inlet of a cooling channel of the blade, the flow of the cool air and the outlet pressure of an air film hole on the surface of the blade;
and 3, carrying out blade inflow calculation and temperature field calculation under the design boundary conditions of the temperature and the pressure of cold air at the inlet of a given blade cooling channel, the flow rate of the cold air and the outlet pressure of a blade surface air film hole, wherein the method comprises the following steps: firstly, obtaining cooling air flow according to pressure difference of an inlet and an outlet of a cooling channel and according to calculation experience correlation calculation of flow coefficients, then obtaining internal heat exchange coefficients of the cooling channel according to calculation experience correlation calculation of the heat exchange coefficients, loading internal and external boundary conditions on a calculation model of the blade on the basis, and sequentially completing temperature field and strength calculation of the blade; obtaining a double-wall impact turbulent flow cooling structure meeting the blade cooling design requirements through continuous iteration until calculation, wherein the blade cooling design requirements comprise cold air flow requirements, blade temperature and strength;
the calculation experience correlation formula of the flow coefficient of the double-wall impact turbulent cooling structure is as follows:
when the turbulent flow column is arranged in sequence: c (C) d ＝0.218582Re 0.129919 Kn 0.042870 (H/D) 0.384319
When vortex column fork row: c (C) d ＝0.205671Re 0.134878 Kn 0.042011 (H/D) 0.398420
The calculation experience correlation of the heat exchange coefficient of the double-layer wall impact turbulent cooling structure is as follows:
when the turbulent flow column is arranged in sequence: nu= 0.020332Re 0.879857 (H/D) -0.192851
When vortex column fork row: nu= 0.019616Re 0.879260 (H/D) -0.168356
C d Nu is the Nuzier number, re is the Reynolds number, kn is the Knudsen number, and H/D is the impact distance and aperture ratio; simulating a double-wall turbine blade corresponding to the core size, the turbulent flow column and the cooling channel size meeting the correlation requirements to obtain a temperature field of the blade, and judging whether the temperature and the stress of the blade are in the temperature and strength range of the material; if not, adjusting the geometric parameter value until the double-wall combined cooling structure meets the requirement; step 4, according to the core size meeting the relation in the step 3, turbulent flow column and coldThe size of the cooling channel is prepared into a blade core with a turbulent flow column and an inner wall cooling channel structure, and then a double-wall turbine blade casting molding is carried out by adopting a lost wax method.
Further, before the step 4 of lost wax casting, the core placed in the casting mold is subjected to reinforcement pretreatment, and the method specifically comprises the following steps:
A. pre-selecting front and rear edges of the core and a part with a flat curved surface of the core, and applying a core positioning tool;
B. pre-hanging wax at the weak part of the core strength, wherein the weak part of the core strength is determined through ANSYS software calculation;
C. and (3) performing wax pattern compression molding on the core after the pre-waxing treatment, and arranging wax pattern supporting pieces at the upper edge plate and the lower edge plate of the wax pattern.
In the step B, the strength calculation is carried out by inputting design temperature, vibration, air flow and cold efficiency coefficient parameters into ANSYS software and adopting a plane183 with a node generalized plane strain unit in a belt, the area with equivalent stress of more than 420MPa or mechanical stress of more than 160MPa is determined to be the weak part of the double-wall turbine blade, and the weak corresponding position is reinforced by adopting a pre-waxing method.
Further, the wax hanging filling thickness is controlled to be in the range of 0.3mm-1.0mm, and the cooling time is not less than 8 hours.
Further, the support member is square, round or irregular in shape, and has a cross-sectional area ranging from 2.25mm 2 -6mm 2 . Compared with the prior art, the invention has the beneficial effects that:
1. according to the invention, the core size suitable for the double-wall turbine blade is determined through introducing flow coefficient and heat exchange coefficient calculation experience association, so that the cooling effect is better while the strength requirement is met;
2. the pre-hanging wax filling method before the core is used for pressing the wax mould ensures high-efficiency cooling and avoids the defects of deformation or fracture and the like of the micro-scale structure in the casting process; by arranging the wax pattern support piece structure, the uniformity and deformation of the wall thickness in the casting process are reduced; the mode of arranging the core positioning tool at the front edge, the rear edge, the curved surface flat position and the like of the core ensures that the wax mould and the core are reliably positioned and have small deformation.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic illustration of a microscale channel cooling profile for a double-walled turbine blade of example 1 or 2;
FIG. 2 is a schematic diagram of a medium core positioning tooling of example 1 or 2;
FIG. 3 is a schematic view showing the structure of a wax pattern support in example 1 or 2;
1, a core; 2. an impingement hole; 3. a turbulent flow column; 4. positioning a tool; 5. a support; 6. a wax pattern; 7. and (5) air film holes.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the present disclosure, when the following description of the embodiments is taken in conjunction with the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. The present application may be embodied or carried out in other specific embodiments, and the details of the present application may be modified or changed from various points of view and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
Example 1
Referring to fig. 1-3, a method of manufacturing a double-walled turbine blade includes the steps of:
step 1, determining matrix materials and dimensions of a double-wall turbine blade core 1 and cooling design parameters of the blade according to the design dimensions and cooling design requirements of the double-wall turbine blade, wherein the cooling design parameters comprise cold air temperature Tc and pressure Pc of an inlet of a cooling channel in the blade, cooling air flow Mc and outlet pressure Pg of a gas film hole 7 on the surface of the blade;
firstly, according to the pressure difference (Pc-Pg) of an inlet and an outlet of a cooling channel, calculating according to a flow coefficient calculation formula to obtain cooling air flow, then calculating according to a heat exchange coefficient calculation experience correlation to obtain an internal heat exchange coefficient of the cooling channel, loading internal and external boundary conditions on a calculation model of the blade on the basis, and sequentially completing temperature field and strength calculation of the blade. The double-wall impact turbulent cooling structure meeting the blade cooling design requirements (cold air flow, blade temperature and strength) is obtained through continuous iteration until calculation;
the following calculation formula is adopted for verification when the spoiler column 3 is arranged in parallel:
C d ＝0.218582Re 0.129919 Kn 0.042870 (H/D) 0.384319
Nu＝0.020332Re 0.879857 (H/D) -0.192851
the following calculation formula is adopted for verification when the spoiler column 3 is arranged in a fork manner:
C d ＝0.205671Re 0.134878 Kn 0.042011 (H/D) 0.398420
Nu＝0.019616Re 0.879260 (H/D) -0.168356
C d is a streamThe quantity coefficient, nu is the Nuzier number, re is the Reynolds number, kn is the Knudsen number, and H/D is the impact distance and aperture ratio;
and 4, preparing a blade core 1 which can be cast into a structure with the turbulence post 3 and the inner wall cooling channel according to the size of the core 1, the turbulence post 3 and the cooling channel which meet the correlation type in the step 3, and then adopting a lost wax method to cast and mold the double-wall turbine blade.
In this embodiment, according to the flow coefficient and heat exchange coefficient, the experience correlation is calculated, and whether the size of the core 1, the turbulent flow column 3 and the cooling channel meet the correlation requirement is verified, so that the micro-scale structure of the double-wall turbine blade core 1 is obtained in an optimized manner, the double-wall turbine blade is obtained through lost wax casting, and the double-wall turbine blade structure with a more efficient cooling effect can be obtained.
Before the lost wax casting, the step 4 is to carry out reinforcement pretreatment on the core 1 placed in the casting mould, and specifically comprises the following steps:
A. pre-selecting the front edge and the rear edge of the core 1 and the part of the core 1 with a flat curved surface, and applying a positioning tool 4 of the core 1;
B. pre-hanging wax at the weak strength of the core 1, wherein the weak strength of the core 1 is determined through ANSYS software calculation;
C. the core 1 after the pre-waxing treatment is subjected to compression molding of the wax pattern 6, and the supporting pieces 5 of the core 1 are arranged at the upper edge plate and the lower edge plate of the wax pattern 6.
Through the steps, the wax hanging process is carried out at the weak part of the mold core 1 in advance, so that the mold core is subjected to high casting pressure, the casting qualification rate is improved, and the more efficient cooling effect of the turbine double-wall blade is achieved while the manufacturing strength requirement is met. Meanwhile, various defects in the casting process can be reduced and the qualification rate of finished products can be improved by optimally designing a core 1 supporting tool and arranging a supporting piece 5 at the flat curved surface part to support the core 1.
Example 2
Referring to fig. 1-3, the embodiment provides a manufacturing method of a double-wall turbine blade, which specifically comprises the following technical scheme:
1. core material determination
The matrix material of the core 1 is the basis for manufacturing a qualified double-walled turbine blade. In this embodiment, the core 1 base material alpha-Al is selected 2 O 3 The purity is more than or equal to 96%, the content is controlled to be more than or equal to 88wt%, and the granularity is in the range of 30-53 um. The mineralizer can be mullite or SiO 2 The content is controlled to be more than or equal to 1.8 weight percent, and the rest components are plasticizer materials.
2. Core design of efficient impact-turbulent flow column combined cooling structure
The core 1 design of an impingement-turbulator combined cooling structure with efficient cooling performance is critical to the design of a double-walled turbine blade, as shown in FIG. 1. Aiming at a combined cooling structure with the diameter of an impact hole 2 of 0.4mm-0.6mm, the interval of the impact hole 2 of 2-3 times of the aperture, the height of a double-layer wall impact cavity of 0.5mm-1.0mm and the diameter of a turbulent flow column 3 of 0.45mm-0.65mm, under a given design boundary condition, according to flow coefficient and heat exchange coefficient calculation experience correlation, a calculation formula of the staggered arrangement of the turbulent flow column 3 is adopted to verify whether the size of a core 1, the size of the turbulent flow column 3 and the size of a cooling channel meet correlation requirements;
C d ＝0.205671Re 0.134878 Kn 0.042011 (H/D) 0.398420
Nu＝0.019616Re 0.879260 (H/D) -0.168356
C d as a flow coefficient, nu is the nuSier number: nu=h×d/K, where h is the convective heat transfer coefficient, K is the thermal conductivity of the cooling air, and Re is the reynolds number: re=ρvd/μ, where v, ρ, μ are the flow rate, density, and coefficient of viscosity of the cooling air, respectively, D is the impingement hole 2 aperture; kn is the knudsen number: kn=λ/D, where λ is the molecular mean free path of the cooling air; H/D is the impact distance to aperture ratio; in this embodiment, the Reynolds number Re is 1000-10000, and the Knudsen number Kn is 1.2X10 -5 -3.5×10 -5 The range of the impact distance and the aperture ratio H/D is 2-3.
According to the correlation, preliminarily determining the size of the core 1 meeting the correlation requirement and the sizes of the spoiler column 3 and the cooling channel as the size of the core 1 of the double-wall combined cooling structure; in the embodiment, the temperature field of the blade is obtained by simulating the double-wall turbine blade corresponding to the size of the core 1, the size of the turbulent flow column 3 and the size of the cooling channel which meet the correlation requirements, and whether the temperature and the stress of the blade are in the temperature and strength range of the material is judged; and if the material performance requirements are met, adjusting the geometric parameter value until the double-wall combined cooling structure meets the requirements, and further ensuring that the turbine double-wall blade has a more efficient cooling effect while meeting the material performance requirements.
Through the steps, the size of the core 1, the size of the spoiler column 3 and the cooling channel which meet the associated requirements are finally determined.
3. Core forming
Preparing a mold core 1 capable of casting and forming a turbulent flow column 3 and an inner wall cooling channel for the size of the mold core 1 and the sizes of the turbulent flow column 3 and the cooling channel which meet the correlation type, material temperature resistance and strength range; the present embodiment can mold the core 1 in an initial state according to the core 1 mold using a photo-curing molding technique or other similar technique (e.g., 3D printing).
4. Core sintering
Shrinkage problems of the core 1 during sintering greatly affect the yield of the final double-walled turbine blade part. Thus, the following sintering parameters of the core 1 are employed in this example: the formed core 1 is sintered and formed at 1260 ℃ to 1290 ℃ and 4 to 10 hours by adopting the heating rate of 50 ℃ to 100 ℃/h. By the molding method of the above-described preferable and determined parameters, the shrinkage of the core 1 can be stably controlled within 0.5% to 0.8%. By combining the shrinkage ratio, the size adaptability of the core 1 is enlarged in advance, and the final molding accuracy requirement can be satisfied.
5. Positioning of cores
In the embodiment, the core 1 has a structural form that forms a multi-layer structure core 1, generally, when the multi-layer core 1 is pressed by a wax pattern 6 (i.e. the core 1 is coated inside the wax pattern 6, after the blade is cast by a lost wax method, the core is removed by acid, alkali or other auxiliary agents capable of eroding the core 1 to obtain the blade with cooling structures such as cooling channels, turbulence columns 3, impact holes 2, etc.), because the positioning between the multi-layer cores 1 is only performed by partial turbulence column 3 structures, etc., it is noted that the size of the turbulence columns 3 of the double-layer turbine blade is smaller, the positioning and small deformation requirements in the manufacturing process are difficult to be satisfied, and the casting process often has the problems of under casting, core misalignment, core leakage, etc.
By using the strength and damage tolerance assessment methods for double-walled blades, the blade is allowed to have a certain crack propagation life, so that the crack does not propagate rapidly at relatively low leading and trailing edge stress levels. In this embodiment, the design of the tooling 4 for positioning the clad core 1 is performed by selecting the front and rear edges and the flat curved surface portion of the core 1. As shown in fig. 2, positioning tools 4 are arranged at the front and rear edge positions of the blade of the core 1 and the position of the curved surface of the core 1, so that reliable positioning is ensured, the number of turbulent flow columns 3 is increased, the compaction of the multi-layer core 1 is performed, the strength is ensured, and the deformation is reduced. The number of positioning points can be set to 6-8 according to different conditions.
6. Core wax-hanging filling
Generally, the size of the turbulence post 3 on the turbine blade core 1 is 1.2mm or more, and for a double-wall turbine blade, the size of the opening is too large, so that the overall structural strength is affected; at the same time, oversized designs fail to meet the more efficient cooling requirements of double-walled turbine blades. In this embodiment, before the step of pressing the core 1 to the wax pattern 6, the core 1 is filled with the pre-hanging wax, particularly at the weak portion of the core 1, typically at the structures such as the spoiler column 3 and the wall surface and the support having the thickness of 0.3mm to 0.8 mm. In the embodiment, the strength calculation is performed by inputting design temperature, vibration, air flow and cold efficiency coefficient parameters into ANSYS software and adopting a plane183 with a node generalized plane strain unit in a belt, the area with equivalent stress of more than 420MPa or mechanical stress of more than 160MPa is determined to be the weak part of the double-wall turbine blade, and the weak corresponding position is reinforced by adopting a pre-wax hanging method, so that the deformation, crack and fracture of the mold core 1 are avoided. The wax mould 6 formed by the method reinforces and protects the weak part, plays a role in reinforcing the weak structural strength of the core 1 and reducing deformation, and prevents the defects of deformation, fracture and the like caused by higher casting pressure in the manufacturing process of the double-wall turbine blade. In the embodiment, the thickness of the wax coating and filling is generally controlled within the range of 0.3mm-1.0mm, and the cooling time is not less than 8 hours.
7. Wax mould support
The wall thickness of the double-wall turbine blade is relatively thin, the strength of the double-wall turbine blade under the traditional structural design is difficult to maintain under high casting pressure, and structures such as an upper flange plate and a lower flange plate are easy to deform in the manufacturing process, so that the out-of-tolerance and rejection of parts are caused. Therefore, the following design is made in this embodiment: the supporting pieces 5 of the core 1 are arranged at the upper and lower edge plates of the wax mould 6 and are used for supporting the weak structure of the wax mould 6, as shown in figure 3, the shape adopts square, round or special-shaped, and the cross section area is in the range of 2.25mm 2 -6mm 2 . After the design is adopted, the overall strength and the structure of the wax pattern 6 are enhanced, and the casting qualification rate is obviously improved.
8. Wax pattern casting
In the embodiment, a lost wax method is adopted for casting and forming the double-wall turbine blade.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. A method of manufacturing a double-walled turbine blade comprising the steps of:
step 1, determining a double-wall turbine blade core base material and size and cooling design parameters of a blade according to the design size and cooling design requirements of the double-wall turbine blade, wherein the cooling design parameters comprise the temperature and pressure of cool air at the inlet of a cooling channel of the blade, the flow of the cool air and the outlet pressure of an air film hole on the surface of the blade;
step 2, determining the height H of a double-layer wall impact cavity and an initial impact turbulence cooling structure according to the wall thickness design of the blade, wherein the impact turbulence cooling structure comprises an impact hole aperture D, a hole pitch P, turbulence columns and cooling channel dimensions;
and 3, carrying out blade inflow calculation and temperature field calculation under the design boundary conditions of the temperature and the pressure of cold air at the inlet of a given blade cooling channel, the flow rate of the cold air and the outlet pressure of a blade surface air film hole, wherein the method comprises the following steps: firstly, obtaining cooling air flow according to pressure difference of an inlet and an outlet of a cooling channel and according to calculation experience correlation calculation of flow coefficients, then obtaining internal heat exchange coefficients of the cooling channel according to calculation experience correlation calculation of the heat exchange coefficients, loading internal and external boundary conditions on a calculation model of the blade on the basis, and sequentially completing temperature field and strength calculation of the blade; obtaining a double-wall impact turbulent flow cooling structure meeting the blade cooling design requirements through continuous iteration until calculation, wherein the blade cooling design requirements comprise cold air flow requirements, blade temperature and strength;
the calculation experience correlation formula of the flow coefficient of the double-wall impact turbulent cooling structure is as follows:
when the turbulent flow column is arranged in sequence: c (C) d ＝0.218582Re 0.129919 Kn 0.042870 (H/D) 0.384319
When vortex column fork row: c (C) d ＝0.205671Re 0.134878 Kn 0.042011 (H/D) 0.398420
The calculation experience correlation of the heat exchange coefficient of the double-layer wall impact turbulent cooling structure is as follows:
when the turbulent flow column is arranged in sequence: nu= 0.020332Re 0.879857 (H/D) -0.192851
When vortex column fork row: nu= 0.019616Re 0.879260 (H/D) -0.168356
C d Nu is the Nuzier number, re is the Reynolds number, kn is the Knudsen number, and H/D is the impact distance and aperture ratio; simulating a double-wall turbine blade corresponding to the core size, the turbulent flow column and the cooling channel size meeting the correlation requirements to obtain a temperature field of the blade, and judging whether the temperature and the stress of the blade are in the temperature and strength range of the material; if not, adjusting the geometric parameter value until the double-wall combined cooling structure meets the requirement; step 4, preparing a blade core which can be cast into a structure with the turbulence column and the inner wall cooling channel according to the core size, the turbulence column and the cooling channel size which meet the correlation in the step 3, and then adopting a wax losing methodAnd casting and forming the double-wall turbine blade.
2. The method of manufacturing a double-walled turbine blade according to claim 1, wherein the reinforcing pretreatment of the core placed in the casting mold before the lost wax casting in step 4 comprises the steps of: A. pre-selecting front and rear edges of the core and a part with a flat curved surface of the core, and applying a core positioning tool; B. pre-hanging wax at the weak part of the core strength, wherein the weak part of the core strength is determined through ANSYS software calculation; C. and (3) performing wax pattern compression molding on the core after the pre-waxing treatment, and arranging wax pattern supporting pieces at the upper edge plate and the lower edge plate of the wax pattern.
3. The method of manufacturing a double-walled turbine blade according to claim 2, wherein in step B, the strength calculation is performed by using the in-band node generalized plane strain unit plane183 by inputting design temperature, vibration, air flow and coefficient of cooling parameters in ANSYS software, the area where the equivalent stress is 420MPa or more or the mechanical stress is 160MPa or more is determined to be the weak part of the double-walled turbine blade, and the reinforcing is performed by using a pre-wax-hanging method at the weak corresponding position.
4. A method of manufacturing a double-walled turbine blade according to claim 3 wherein the wax-coating thickness is controlled in the range of 0.3mm-1.0mm and the cooling time is not less than 8 hours.
5. A method of manufacturing a double-walled turbine blade according to claim 2 wherein the support member is square, circular or profiled in shape with a cross-sectional area in the range of 2.25mm 2 -6mm 2 。
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